Shock Wave Boundary Layer Interaction
Unstructured Validation
Freestream Mach 5, 10 degree deflection angle

GAS 1.400 .72 .9 1716.

/ SPAWN ------------------------------------------------
SPAWN "./post_process" FREQUENCY 2000

/ BOUNDARY CONDITIONS ----------------------------------
Freestream TOTAL conditions 5.  307.48  738.00  0.0 0.0
Downstream pressure extrapolate zone all

Wall Temperature 540.00 zone all


/ VISCOUS TERMS ----------------------------------------
/turbulence spalart
turbulence sst 
/Turbulence chien
/k-e order 1
/k-e variable cmu off
/k-e compressibility none
/k-e initialize from existing
/k-e maximum turbulent viscosity 20000
/k-e turbulent reference velocity 5.0

mut limiter 50

/ NUMERICS ---------------------------------------------
cycle 12000
iterations per cycle 1
converge order 10
cfl auto decrease 2 cflmin 1 cflmax 100
/dq limiter on relax 0.5
fixer zone all

rhs hlle second
rhs viscous thin-layer
implicit boundary on
implicit ugauss line exact_lhs viscous_jacobian full converge frequency 11 subiterations 6
gradient least_squares

tvd barth 3.0

SOLVER-STAGES
 RESTART_STAGES
 STEP FIRST
  SOLVER NAVIER-STOKES
   SET RHS TO HLLE FIRST
   SET CYCLES TO 1000
  END SOLVER
 END STEP
 STEP SECOND
 END STEP
END SOLVER-STAGES


write variables cf
write walldistance

/ OPTIONS ----------------------------------------------
/DEBUG  3  1  / Print 'actual' RHS residual
/DEBUG 41  1  / Enable Implicit coupling, for running dedicated
/DEBUG 42  1  / Cycle-time efficiency, gradient calculated once between the N-S and turbulence mode pass, not coupled
/DEBUG 46  6  / Face gradient correction, more stable viscous flux discretization than 46 1
/TEST 51 50   / Set mu_t limit to 50,000

END